CN104229156A - Method of installing a fixture - Google Patents
Method of installing a fixture Download PDFInfo
- Publication number
- CN104229156A CN104229156A CN201410261838.6A CN201410261838A CN104229156A CN 104229156 A CN104229156 A CN 104229156A CN 201410261838 A CN201410261838 A CN 201410261838A CN 104229156 A CN104229156 A CN 104229156A
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- Prior art keywords
- anchor fitting
- airframe structure
- digital model
- anchor
- head
- Prior art date
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- 238000004519 manufacturing process Methods 0.000 claims abstract description 34
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- 239000000463 material Substances 0.000 claims description 9
- 230000004927 fusion Effects 0.000 claims description 7
- 238000009434 installation Methods 0.000 claims description 7
- 229920000642 polymer Polymers 0.000 claims description 7
- 230000005496 eutectics Effects 0.000 claims description 6
- 239000003550 marker Substances 0.000 claims description 6
- 238000000465 moulding Methods 0.000 claims description 5
- 239000000843 powder Substances 0.000 claims description 5
- 239000004676 acrylonitrile butadiene styrene Substances 0.000 claims description 4
- 229920001169 thermoplastic Polymers 0.000 claims description 4
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- 238000010146 3D printing Methods 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C64/00—Additive manufacturing, i.e. manufacturing of three-dimensional [3D] objects by additive deposition, additive agglomeration or additive layering, e.g. by 3D printing, stereolithography or selective laser sintering
- B29C64/10—Processes of additive manufacturing
- B29C64/106—Processes of additive manufacturing using only liquids or viscous materials, e.g. depositing a continuous bead of viscous material
- B29C64/118—Processes of additive manufacturing using only liquids or viscous materials, e.g. depositing a continuous bead of viscous material using filamentary material being melted, e.g. fused deposition modelling [FDM]
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F5/00—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F7/00—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression
- B22F7/06—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools
- B22F7/062—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools involving the connection or repairing of preformed parts
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C64/00—Additive manufacturing, i.e. manufacturing of three-dimensional [3D] objects by additive deposition, additive agglomeration or additive layering, e.g. by 3D printing, stereolithography or selective laser sintering
- B29C64/10—Processes of additive manufacturing
- B29C64/106—Processes of additive manufacturing using only liquids or viscous materials, e.g. depositing a continuous bead of viscous material
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16M—FRAMES, CASINGS OR BEDS OF ENGINES, MACHINES OR APPARATUS, NOT SPECIFIC TO ENGINES, MACHINES OR APPARATUS PROVIDED FOR ELSEWHERE; STANDS; SUPPORTS
- F16M13/00—Other supports for positioning apparatus or articles; Means for steadying hand-held apparatus or articles
- F16M13/02—Other supports for positioning apparatus or articles; Means for steadying hand-held apparatus or articles for supporting on, or attaching to, an object, e.g. tree, gate, window-frame, cycle
Landscapes
- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Materials Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Optics & Photonics (AREA)
- General Engineering & Computer Science (AREA)
- Transportation (AREA)
- Composite Materials (AREA)
- Automatic Assembly (AREA)
Abstract
The invention relates to a method of installing a fixture (1), such as a bracket, in a fuselage structure (F) of an aircraft (A), the method comprising the steps of: providing or generating a three-dimensional digital model (M) of the fixture (1); arranging a head (6) of an additive manufacturing apparatus (7) in the fuselage structure; and forming the fixture (1) in situ in the fuselage structure (F) with the head (6) of the additive manufacturing apparatus (7) based upon the digital model (M) of the fixture (1); wherein the fixture (1) is installed in the fuselage structure (F) by bonding or fusing the fixture (1) to the fuselage structure as the fixture (1) is formed. Also, the invention provides a fixture (1), such as a bracket, which is generated in situ in a fuselage structure (F) of an aircraft based upon a three-dimensional digital model (M), wherein the fixture (1) is bonded or fused to the fuselage structure (F) as the fixture (1) is formed.
Description
Technical field
The present invention relates to a kind of on the body construction of the vehicle, especially the body of aerocraft or spacecraft or airframe structure are installed the method for the anchor fitting of such as support, for relative to this structure installment or articles or system.The invention still further relates to the anchor fitting of such as support, to be arranged in the vehicle or on, especially on aerocraft or spacecraft or in, and therefore relate to the vehicle itself being incorporated to this anchor fitting.Be noted that term used herein " spacecraft " comprises satellite and space station module, and rocket module or parts.
Background technology
Such as there is the object of the electricity system of pipeline and cable and/or the installation of system in boats and ships, aviation or automobile application and be usually directed to need to be fixed to structure (such as, vehicle chassis or fuselage shell structural) for the fixing device for installing of these systems of rear support or the use of support.By convention, these anchor fittings are via the fastener of such as rivet, clip or spiral nail or be fixed to this structure via adhesives.
Some shortcomings of the machanical fastener of such as rivet and spiral nail comprise: anchor fitting or support need to position relative to hole for the hole of fastener, anchor fitting needs and need tightening operation so that fixation fastener subsequently.Depend on specific application, also can need subsequently around fastener and hole environmental seal anchor fitting or support.These steps relate to process costs naturally.Some shortcomings that adhesives connects comprise: anchor fitting or support and connecting surface both may need pretreatment, such as roughening and/oil removing, applying adhesive is needed to operate, with the operation that followed by location and fixing device for installing or support under applying pressure.These steps relate to process costs again.
Summary of the invention
Therefore, the object of the present invention is to provide a kind of newly and improve one or more methods or technology for overcoming the problems referred to above.In particular, provide a kind of method of fixing device for installing or support in the airframe structure of aerocraft or spacecraft newly, make can to promote faster in this way and/or process automatically.
According to the present invention, provide as the method for claim 1 and fixing device for installing according to claim 8 and corresponding anchor fitting for by object or system relative to structure installment or connection, the structure especially in boats and ships, aviation or automobile application.Further, according to the present invention, also provide the vehicle of such as aerocraft as claimed in claim 12.Describe multiple preferred feature in the dependent claims.
Therefore according on the one hand, the invention provides a kind of on the body construction of the vehicle, the airframe structure of especially aerocraft or spacecraft installed the method for the anchor fitting of such as support, comprise step:
There is provided or generate the three-dimensional digital model of anchor fitting;
In this airframe structure or on or near arrange and add the head of manufacturing equipment; With
Digital model based on anchor fitting uses or on airframe structure, forms anchor fitting via the head of this interpolation manufacturing equipment in original place;
By formed anchor fitting time by anchor fitting (such as mechanically, or via combination or bonding or fusion) be connected to airframe structure fixing device for installing on airframe structure.
In this way, along with the formation of anchor fitting self automatically can be fixed the installation of device substantially.Therefore, the method provides maximum alerting ability in fuselage assembling process, and does not need to manufacture independent anchor fitting or support discretely or in outside.Also without any need for the spare components of storage, because directly form anchor fitting by digital model during installation.Similarly, do not need non-flight (non-flying) part, such as, this non-flight part may be needed to be fixed to by support during solidification process in structure and be then removed this non-flight part afterwards.Correspondingly, the design of anchor fitting can comprise the four corner of form of distortion, and can easily adapt to when design parameters changes or revise.
In a preferred embodiment, in airframe structure, form the step of anchor fitting comprise by setting up anchor fitting with the head generation adding manufacturing equipment and/or multiple layers of setting up anchor fitting in turn in original place.In this case, multiple layers of anchor fitting can be deposited on airframe structure in turn, make it possible to set up anchor fitting based on digital model by these layers until its final three dimensional form.Correspondingly, in a preferred embodiment, step anchor fitting being connected to structure comprises: when in the structure of the vehicle generate and/or deposit anchor fitting multiple layers in one or more time, by the one or more combination in multiple layers of anchor fitting or bonding or airframe structure can be fused to.Alternatively, or additionally, to generate in the structure of the vehicle and/or after multiple layers of deposit anchor fitting one or more, can by one or more combination of multiple layers of anchor fitting or bonding or be fused to airframe structure in curing schedule subsequently.But in an additional preferred embodiment, step anchor fitting being connected to structure can comprise: to engage with the some mechanical of structure or to be connected or the mode that coordinates of machinery forms anchor fitting.In fact, step anchor fitting being connected to structure can comprise will in conjunction with or bonding or fusion and mechanical engagement or Connecting groups be combined.
In a preferred embodiment, the method is designed or is applicable to use together with the structure comprising composite material, especially with the polymer composites comprising fiber and strengthen, the structure that such as glass fibre adds strength polymer (GFRP) composite material or carbon fiber reinforced polymers (CFRP) composite material uses together.Therefore, the material that interpolation manufacturing equipment can be configured to be fused or combine by the poly-mer being suitable for strengthening with the fiber in structure or bonded generates or forms anchor fitting.But, should be realized that, described method can also be performed in the situation of body construction comprising the metal be usually used in traditional fuselage or frame and airframe structure, make to add the material that manufacturing equipment is configured to by fusing with metal construction or combine or bond and generate or form anchor fitting.Except the fusion that realizes via described method or combination or bonding connection, auxiliary machanical fastener such as such as rivet, screw, bolt etc. can also be used to fix anchor fitting; These additional fasteners may be used for the connection of reinforcing anchor fitting and vehicle configurations.
In the especially preferred embodiment of the present invention, use add manufacturing equipment formed or the step of setting up anchor fitting comprise following in any one or multiple: fusion deposit moulding (FDM), laser sintered (LS), selectivity heat-agglomerating (selective heat sintering, and stereolithography (stereo-lithography, SLA) SHS).These technology can be referred to as three-dimensional (3D) and print.In the situation of stereolithography (SLA), anchor fitting then will be formed by photopolymer material or photopolymerizable material, such as can UV curing or ultraviolet-sensitive poly-mer.In the situation of fusion deposit moulding (FDM) process, anchor fitting can be formed by the curable polymer of such as acrylonitrile-butadiene-styrene (ABS) or high density polyethylene (HDPE) (HDPE) or thermoplastic polymer, or form anchor fitting by the metal of such as eutectic metal (eutectic metal).In the situation of selectivity heat-agglomerating (SHS) or laser sintered (LS), anchor fitting can be formed by the almost any metal alloy usually provided with powder or particle form, but also can by a series of poly-mers formation anchor fittings that also can be powder or particle form.The example being suitable for using method of the present invention to manufacture the poly-mer of anchor fitting continuously comprises trade mark for NanoTool
tM, NanoForm
tMand ProtoTherm
tMdSM
product.These poly-mers are ultraviolet solidifiable, make them can by hardening with UV-irradiation after deposit becomes the net shape of anchor fitting.In this case, these DSM
poly-mer usually has 79 to 121N/mm after UV cured
2bending stiffness in scope and 62 to 78N/mm
2extensional rigidity in scope.
In especially preferred embodiment, the three-dimensional digital model of anchor fitting comprises about anchor fitting in structure or the data of structural particular location or desired locations.Therefore, the step forming anchor fitting in original place preferably includes in based on digital model locates about the data of particular location or desired locations the head adding manufacturing equipment in structure or in structure.For this reason, body or airframe structure can comprise for providing the one or more reference markers with the spatial correspondences of the reference point in the digital model of anchor fitting.One or more sensor can be set, for detection and Identification reference marker and then based on the head of the reference marker location interpolation manufacturing equipment of detection and Identification.
Add the head of manufacturing equipment or the location of interpolation manufacturing equipment and move preferably computer-controlled.Such as, interpolation manufacturing equipment or its head can be arranged on robot assembly or robots arm, and robot assembly or robots arm can be controlled to move the head with fixing aid based on the three-dimensional digital model of anchor fitting.In this way, anchor fitting or support locating very accurately in body construction or on body construction can be realized, and there is high-caliber repeatability.
Although the above concrete vehicle with reference to such as aerocraft or spacecraft describe method of the present invention, one skilled in the art would recognize that the present invention also can be applied in the structure of non-vehicle.Such as, the present invention is also provided in such as wind turbine or the method for installing the anchor fitting of such as support on the post of antenna (such as communication or TV antenna) or the fixed sturcture of tower, building or other this structures.In addition, although method fixing device for installing of the present invention can be used during manufacturing structure itself, when post, tower, building or space station also can subsequently such as by climbing or climbing robot assembly at original place fixing device for installing.
Therefore, according to another aspect, the invention provides a kind of method of installing the anchor fitting of such as support on body or structure, comprise step:
There is provided or generate the three-dimensional digital model of anchor fitting;
On this structure or neighbouring layout add the head of manufacturing equipment; With
Digital model based on anchor fitting uses or structurally forms anchor fitting in original place via the head adding manufacturing equipment;
Wherein when formed anchor fitting time by anchor fitting being connected to structure structurally fixing device for installing.
By adopting said method in space via being equipped with the robot assembly adding manufacturing equipment or three-dimensional printer, such as with on the body shell of the space station of orbiting motion or outside perform maintenance or erection work, astronaut can in order to avoid necessity of space walk and relevant risk thereof.In other words, method of the present invention can be used via robot fixing device for installing, robot can in space environment in the clear and operate with there is no risk.Therefore, mobile robot device, such as climbing or climbing robot may be used for performing method of the present invention.
In especially preferred embodiment of the present invention, can form and/or revise the digital model of anchor fitting during installation process.When performing described method such as to carry out the maintenance of the part of structure, before the accurate shape can determining the anchor fitting needed and/or size, may first need check and/or assess part to be repaired.For this reason, method of the present invention can comprise step: check that the part of structure is with assessment and/or geometric configuration and/or the size of determining required anchor fitting, then provides based on the result checked or formed three-dimensional (3D) digital model of anchor fitting.Therefore robot assembly can comprise checkout facility, and such as video camera and/or one or more sensor are in order to inspection and/or the part checking interested structure.
The extension of above design comprises such as arranging on robot or providing adds manufacturing equipment or 3D chopping machine, and it also generates or formed structure anchor fitting or element for installing structurally the body shell of space station (such as, on).This anchor fitting or element also can provide with the form of track or guide rail, and then track or guide rail affect or determine moving or advancing of robot itself.These elements such as can be designed to drafting or limiting robot extremely may need to take the particular location of maintenance or the path of assigned address.
According to another aspect, the invention provides a kind of anchor fitting of such as support, its based on three-dimensional digital model at structure (especially vehicle body construction, the frame of such as aerocraft or space vehicle or fuselage) in or upper at autochthonous, wherein when formation anchor fitting, this anchor fitting is connected to this structure.Bright as noted earlier, preferably when forming anchor fitting, anchor fitting combines or bonds or be fused to structure, but alternatively, it can mechanically connect.Should be realized that, " anchor fitting " is in the context of the present invention not limited to support or similar such installation elements, but can also comprise the inner cover parts of structure or the vehicle or the housing in cabin or lining panel.
In a preferred embodiment, anchor fitting comprises multiple layers of generation or deposit in turn, and they are combined or bond or be fused to body or airframe structure.Bright as noted earlier, anchor fitting can be formed by polymeric material, such as can ultraviolet-cured polymers, or thermoplastic polymer, such as acrylonitrile-butadiene-styrene (ABS) or high density polyethylene (HDPE) (HDPE), or formed by the metal of such as eutectic metal, comprise and being formed by one or more metal powders.In addition, in especially preferred form of the present invention, the position of anchor fitting in airframe structure or location are based on digital model.
According to another aspect, the invention provides a kind of vehicle, such as aerocraft or spacecraft, it has with at least one according to the body of the anchor fitting of any one in multiple embodiment described above or airframe structure, and the body preferably had with multiple such anchor fitting or airframe structure.For this reason, the vehicle of the present invention can be any one in multiple known shaped traffic device, include but not limited to train, automobile, truck, city motor bus, steamer, ship, spacecraft, helicopter and/or space vehicle.Therefore the body construction of the vehicle can be chassis or the framework of the vehicle.
Accompanying drawing explanation
In order to complete understanding the present invention and advantage thereof more, with reference to accompanying drawing, exemplary embodiment of the present invention is described in further detail in the following description, Reference numeral identical in the accompanying drawings represents identical parts, wherein:
Fig. 1 be aerocraft according to an embodiment of the invention just in the diagrammatic side view of fixing device for installing or the fuselage of support or the part of fuselage shell structural.
Fig. 2 illustrates according to an embodiment of the invention just the fuselage of Fig. 1 or four diagrammatic side view (a) to (d) of fuselage shell structural of fixing device for installing or support.
Fig. 3 schematically illustrates according to specific embodiment fixing device for installing or the method for support or the three phases (i) of technology to (iii);
Fig. 4 is the diagram of circuit of the method schematically illustrated according to preferred embodiment;
Fig. 5 is the schematic diagram of aerocraft, wherein installs one or more support according to an embodiment of the invention; With
Fig. 6 is according to one embodiment of present invention just at the schematic diagram of the space station of fixing device for installing or element.
Detailed description of the invention
Accompanying drawing is used to provide further understanding of the present invention and is merged in and forms the part of specification sheets.Accompanying drawing illustrates specific embodiment of the present invention and in order to explain principle of the present invention together with specification sheets.Other embodiments of the present invention and the incident advantage of many present invention will be easily familiar with, because they become better understanding with reference to detailed description book below.
Should be realized that, can be useful or necessary in commercially feasible embodiment common and the good element understood there is no need to illustrate so that see these embodiments more abstractively.The element of accompanying drawing does not need to illustrate with being proportional to one another.It should further be appreciated that, the specific action in an embodiment of method and/or step can describe with specific genetic sequence or illustrate, it will be understood by those skilled in the art that simultaneously for this feature of order or specificity also without requiring.Be also to be understood that the term that uses in this specification sheets with express have in they corresponding probing into this term in areal of research or field and express consistent common meaning, except having proposed specific meaning herein.
First with reference to Fig. 1 of accompanying drawing, the system for method according to the present invention fixing device for installing 1 (being the form of support) in the frame or airframe structure F of aerocraft is schematically shown herein.The frame of the aerocraft in the present embodiment or airframe structure F comprise the cambered shell part of fuselage, this part comprises the polymer composites that carbon fiber is strengthened, in this case, this part is supported by the supporting element B extended from the support frame S on even keel vertically extended.In Fig. 1, robot assembly 2 is also shown, it comprises the robots arm 3 with multiple articulation or joint 4, and each joint or joint are at least one degree of freedom and preferably can drive on multiple degree of freedom.Robot assembly 2 itself installs on the direction in the plane perpendicular to Fig. 1 along the motion of translation of track component 5.
Being arranged on, the remote area of robots arm 3 adds the head 6 of manufacturing equipment 7, adds manufacturing equipment 7 and be usually understood and maybe can be called 3D type printer.This interpolation manufacturing equipment 7 with any one operation in known 3D printing technique, such as, can fuse deposit moulding (FDM), laser sintered (LS) or stereolithography (SLA).Especially preferred is in the present embodiment fusion deposit moulding (FDM) equipment 7.The movement of robot assembly 2, and more particularly robots arm 3 (is schematically illustrated by computer controlled via computer processor P via the movement in articulation or joint 4 and its position along track component 5 herein, and shown in Figure 3 below), computer processor P also controls the operation adding manufacturing equipment 7.In order to method according to the present invention starts to install new anchor fitting or support 1, to be moved the desired location Z on head 6 to the body shell F of this equipment 7 along the direction of the arrow in Fig. 1 by robots arm 3.
Go back now with reference to the Fig. 2 (a) in accompanying drawing to 2 (d), shown in the series of four images (a) to (d), in airframe structure F, form or set up the step of anchor fitting or support 1.In the image of Fig. 2 (a), the head 6 being arranged in the FDM equipment 7 of the remote area of robots arm 3 has moved to the near surface of the airframe structure F of the aerocraft being positioned at position Z.In computer processor P, arrange or generate the three-dimensional digital model M of anchor fitting or support 1, and based on the data in this digital model M of support 1, the head 6 of computer processor P then control FDM equipment 7 is deposited on CFRP airframe structure along the direction of arrow in Fig. 2 (a) along multiple layers of the surface movement of housing structure F by polymeric material along with the head 6 of equipment 7.Then, in Fig. 2 (b), one or more layers of L1 of support 1 are deposited on airframe structure F at Z place, desired location, and this layer combined or be fused to CFRP structure F.
Then the head 6 of FDM equipment 7 is moved away main body mechanism F slightly along the direction of the arrow shown in Fig. 2 (b).As shown in Fig. 2 (c), then head 6 can start one or more layer L2 newly of deposited polymer material, multiple layers of L1 before new layer L2 is configured in also sets up thus 3D shape or the form of anchor fitting or support 1.This process of Fig. 2 (d) with reference to accompanying drawing continues, until complete the final 3D shape of support 1.
Referring now to Fig. 3 of accompanying drawing, method is according to a preferred embodiment of the invention illustrated to (iii) with three phases (i) in the drawings.Such as, in Fig. 3 (i), operator O is illustrated as being located at the workstation W place of computer processor P, and computer processor P is engaged in the task of three-dimensional (3D) the digital model M providing and/or generate anchor fitting to be installed or support 1 according to the method for the present embodiment.The computer processor P that computer operation person O works also is responsible for the computer-controlled operation of interpolation the manufacturing equipment 7 and robot assembly 2 described above with reference to Fig. 1 and Fig. 2.
Fig. 3 (ii) schematically illustrates relative to forming the step with mounting bracket 1 airframe structure F positioning robot assembly 2 thereon.Therefore, the one or more tracks 5 of robot assembly 2 in tubulose airframe structure F are moveable, being such as separated or in multiple separation of independent height or separation or independent base plate or layer or independent track 5 one be moveable preferably in fuselage F.At this, airframe structure F can be the tubular shell as shown in Fig. 3 (ii), instead of only housing fragment as shown in Figure 1 or part.In addition, robot assembly 2 can comprise multiple robots arm 3, operates for the multiple diverse location Z places in airframe structure F simultaneously, namely to set up in different positions and to install multiple anchor fitting or support simultaneously.
About the location of robot assembly 2, the digital model M of anchor fitting or support 1 can comprise the data of concrete expectation about particular stent 1 on airframe structure F or desired location Z.Then these data can use with being arranged on together with the reference marker R on airframe structure F, the reference marker R be arranged on airframe structure F preferably can be detected by the sensor (not shown) be arranged on robot assembly 2 and identify to provide spatial correspondences, and this spatial correspondences is used for moving to robots arm 3 (especially adding the head 6 of manufacturing equipment 7) for being formed based on the data in digital model M and installing the tram Z of this particular stent 1 relative to airframe structure F.
Fig. 2 of Fig. 3 (iii) and accompanying drawing is substantially corresponding and be schematically illustrated in that airframe structure F is interior to be expected or the deposit in turn of particular stent 1 at Z place, desired location or layer are set up and installed, and its medium-height trestle 1 is combined simultaneously or be fused to the material of airframe structure F.
Referring now to Fig. 4 of accompanying drawing, show diagram of circuit, it schematically illustrates the step in the method for preferred embodiment again.For this reason, the first frame I in Fig. 4 represents the step of the step of three-dimensional (3D) the digital model M arranging support 1 or three-dimensional (3D) the digital model M of generation support 1, then make computer processor P can use or obtain this digital model M, computer processor P operates and controls the robot assembly 2 that manufacturing installation 7 is added in carrying.Then, the second frame II represents the step based on the position data in digital model M, the head 6 adding manufacturing equipment 7 being moved to the desired location Z of airframe structure F.3rd frame III represents that the digital model M based on the support in computer processor P uses the head 6 of FDM equipment 7 in airframe structure F, form the step of support 1 in original place by setting up support 1 in the mode of multilayer in turn.Last frame IV in accompanying drawing 4 represents when forming support 1 by support 1 being combined or is fused to the step of CFRP airframe structure F connection bracket 1.
According to the above-mentioned explanation of the method, Fig. 5 of accompanying drawing schematically illustrates the aerocraft A with airframe structure F, and wherein method according to the present invention installs at least one anchor fitting or support 1, and preferred multiple anchor fitting or support 1.
On the other hand, with reference to Fig. 6 of accompanying drawing, an alternative embodiment is schematically shown.In this embodiment, the space station T being arranged in track at this moment is performing method of the present invention.Space station T comprises solar collection module C, people lives module H and Anneta module I, and they are all interconnected by structural framing X.In this example, the maintenance of described method execution to the part on Anneta module I is used.Again adopt the robot assembly 2 comprising robots arm 3, robots arm 3 has articulation or the joint 4 of Long-distance Control, and this is avoided needing astronaut to take space walking.Structural framing X can comprise the one or more tracks 5 moving to Anneta module I for guided robot 2.In addition, the end regions that the head 6 of manufacturing equipment 7 or 3 D-printing machine are installed in robots arm 3 is added.In this way, on the T of space station with robot assembly 2 can perform above referring to figs. 1 through 3 methods described to generate and to install new element or anchor fitting 1 to keep in repair Anneta module I.Structural framing X not can be used for track 5 of robot 2, it should be noted that, add manufacturing equipment 7 head 6 can also for method according to the present invention generate on the framework X of space station T and attachment rail component 5 for guided robot assembly 2 to this part of Anneta module I to be repaired.
Although illustrated at this and described specific embodiments of the invention, one skilled in the art would recognize that to there is multiple alternative and/or equivalent embodiment.Should be realized that, exemplary embodiment or exemplary multiple embodiments are only examples, and are not in order to limited field, application or configuration mode by any way.On the contrary, summary of the invention above and detailed description will provide the course diagram easily implementing at least one exemplary embodiment to those skilled in the art, should be appreciated that, layout and the function of the element described in exemplary embodiment when not departing from the scope of appended claim and legal equivalents setting thereof can make multiple amendment or change.On the whole, the application is intended to the whole form of distortion or the modification that cover specific embodiment discussed herein.
In this article, term " comprises ", " comprising ", " containing ", " being contained in ", " having ", " with " and its form of distortion should with comprise (namely not exclusive) meaning understand, process described herein, method, device, equipment or system is made to be not limited to those described features or part or element or step, but can comprise not by stating other elements, feature, part or the step listed, or element, feature, part or step that these processes, method, object or equipment are intrinsic.In addition, term " " used herein and " one ", " one " are construed as and represent one or more or multiple, unless explicitly stated otherwise.And term " first ", " second ", " the 3rd " etc. only for mark, and are not to give numerical requirements to set up the particular hierarchical of the importance of these objects or step or element.
The catalogue of Reference numeral
1 anchor fitting or support
2 robot assemblies
3 robots arms
4 joints or joint or articulation
5 tracks
6 heads
7 add manufacturing equipment
F airframe structure or housing
B supporting element
S support frame
P computer processor
M digital model
Installation site on Z airframe structure or housing
L1 ground floor
The L2 second layer
R reference marker
O operator
W workstation
A aerocraft
T space station
C solar collection module
H people lives module
I Anneta module
X structural framing
Claims (12)
1., in the body or airframe structure (F) of aerocraft or spacecraft or a method for the anchor fitting (1) such as upper installation such as support, comprise the steps:
Generate the three-dimensional digital model (M) of anchor fitting (1);
The head (6) adding manufacturing equipment (7) is arranged in this airframe structure (F); With
Digital model (M) based on anchor fitting (1) forms anchor fitting (1) in original place with the head (6) of this equipment (7) on airframe structure (F);
Wherein pass through when forming anchor fitting (1) anchor fitting (1) to be connected to airframe structure (F) at the upper fixing device for installing (1) of airframe structure (F).
2. the method for claim 1, the step wherein forming anchor fitting (1) in original place comprises sequentially sets up anchor fitting (1), the multiple layers generating and set up anchor fitting (1) preferably by the head (6) with equipment (7) in airframe structure (F) set up anchor fitting (1), and wherein multiple layers of anchor fitting (1) are preferably deposited on airframe structure (F) in turn.
3. method as claimed in claim 1 or 2, the step wherein anchor fitting (1) being connected to airframe structure (F) comprise following at least one: when one or more in the multiple layers generating anchor fitting (1), one or more in multiple layers of anchor fitting (1) combined or be fused to airframe structure (F); And/or form anchor fitting (1) in the mode engaged with the some mechanical of structure (F) or machinery coordinates in original place.
4. method as claimed any one in claims 1 to 3, wherein the three-dimensional digital model (M) of anchor fitting (1) comprises the data about the desired locations of anchor fitting (1) in airframe structure (F), and the step wherein forming anchor fitting (1) in original place comprises the head (6) adding manufacturing equipment (7) based on this digital model (M) in airframe structure (F) inner position.
5. method as claimed in claim 4, wherein airframe structure (F) comprises the reference marker (R) for the spatial correspondences with the reference point in the digital model (M) of anchor fitting (1).
6. the method according to any one of claim 1 to 5, wherein anchor fitting (1) is by such as can the polymeric material of ultraviolet-cured polymers or the such as thermoplastic polymer such as acrylonitrile-butadiene-styrene (ABS) or high density polyethylene (HDPE) (HDPE) being formed, or formed by the metal of such as eutectic metal, described metal comprises metal powder.
7. the method according to any one of claim 1 to 6, wherein add manufacturing equipment (7) be configured for following in any one: fusion deposit moulding (FDM), laser sintered (LS), selectivity heat-agglomerating (SHS) or stereolithography (SLA).
8. the anchor fitting (1) such as such as support, its based on three-dimensional digital model (M) at the body of aerocraft or spacecraft or airframe structure (F) inherent autochthonous, wherein when forming anchor fitting (1), this anchor fitting (1) is connected to, preferred combination or be fused to body or airframe structure (F).
9. anchor fitting (1) as claimed in claim 8, wherein, anchor fitting (1) comprises multiple layers of generation or deposit in turn, and they are combined or be fused to airframe structure (F).
10. anchor fitting (1) as claimed in claim 9, wherein anchor fitting (1) is by such as can the polymeric material of ultraviolet-cured polymers or the such as thermoplastic polymer such as acrylonitrile-butadiene-styrene (ABS) or high density polyethylene (HDPE) (HDPE) being formed, or formed by metals such as such as eutectic metals, described formed to comprise by metals such as such as eutectic metals formed by one or more metal powders.
11. anchor fittings (1) according to any one of claim 8 to 10, wherein the position of anchor fitting (1) in airframe structure (F) is based on digital model (M).
12. 1 kinds of aerocrafts (A) with airframe structure (F), this airframe structure (F) has one or more anchor fitting (1) according to any one of claim 8 to 11.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EP13171838.9 | 2013-06-13 | ||
| EP13171838.9A EP2813432B1 (en) | 2013-06-13 | 2013-06-13 | Method of installing a fixture |
Publications (1)
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|---|---|
| CN104229156A true CN104229156A (en) | 2014-12-24 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410261838.6A Pending CN104229156A (en) | 2013-06-13 | 2014-06-12 | Method of installing a fixture |
Country Status (4)
| Country | Link |
|---|---|
| US (1) | US10214275B2 (en) |
| EP (1) | EP2813432B1 (en) |
| CN (1) | CN104229156A (en) |
| RU (1) | RU2566179C1 (en) |
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| CN106696249A (en) * | 2015-11-13 | 2017-05-24 | 通用汽车环球科技运作有限责任公司 | Additive manufacturing of a unibody vehicle |
| CN106696248A (en) * | 2015-11-13 | 2017-05-24 | 通用汽车环球科技运作有限责任公司 | Additive manufacturing of a body component on a tube frame |
| US10022912B2 (en) | 2015-11-13 | 2018-07-17 | GM Global Technology Operations LLC | Additive manufacturing of a unibody vehicle |
| CN106696249B (en) * | 2015-11-13 | 2019-05-14 | 通用汽车环球科技运作有限责任公司 | The increasing material manufacturing of one chip automobile |
| US10493705B2 (en) | 2015-11-13 | 2019-12-03 | GM Global Technology Operations LLC | Additive manufacturing of a body component on a tube frame |
| CN111044441A (en) * | 2019-12-31 | 2020-04-21 | 中国科学院空间应用工程与技术中心 | Material exposure test box locking mechanism and exposure device |
| CN111044441B (en) * | 2019-12-31 | 2022-04-19 | 中国科学院空间应用工程与技术中心 | Material exposure test box locking mechanism and exposure device |
Also Published As
| Publication number | Publication date |
|---|---|
| EP2813432A1 (en) | 2014-12-17 |
| RU2566179C1 (en) | 2015-10-20 |
| EP2813432B1 (en) | 2017-12-20 |
| US10214275B2 (en) | 2019-02-26 |
| US20140367519A1 (en) | 2014-12-18 |
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